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Dual-redundancy flexible strapdown inertial measurement system

A measurement system and strapdown inertial technology, applied in the field of inertial measurement, can solve problems such as inability to carry manned spacecraft into predetermined orbits, threatening the lives of astronauts, and unable to meet the requirements of manned missions, so as to increase reliability and accuracy, The effect of reducing the effects of random bias

Active Publication Date: 2013-11-27
BEIJING INST OF AEROSPACE CONTROL DEVICES
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Problems solved by technology

If one of the measurement information fails or is out of tolerance, the control system will not be able to guide and control accurately, and the rocket will not be able to accurately send the manned spacecraft into the predetermined orbit, which will eventually threaten the life of the astronauts
At this stage, the strapdown inertial group can no longer meet the manned task requirements, so it is necessary to improve the design of the strapdown inertial group

Method used

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  • Dual-redundancy flexible strapdown inertial measurement system
  • Dual-redundancy flexible strapdown inertial measurement system
  • Dual-redundancy flexible strapdown inertial measurement system

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Embodiment Construction

[0014] Such as figure 1 , 2 As shown, a dual-redundant flexible strapdown inertial measurement system designed by the present invention, two groups of flexible strapdown inertial measurement systems are installed in parallel on the rocket body through a vibration damping bracket, and each group of flexible strapdown inertial measurement systems It consists of three two-degree-of-freedom dynamic tuning gyroscopes and four quartz accelerometers, as well as servo loops and I / F conversion circuits that match the dynamic tuning gyroscopes and accelerometers, such as image 3 As shown, three two-degree-of-freedom dynamically tuned gyroscopes are arranged orthogonally according to the Cartesian coordinate system, three of the four accelerometers are arranged orthogonally according to the Cartesian coordinate system, and the fourth accelerometer is arranged obliquely The included angles between the three accelerometers arranged in an orthogonal manner are all 54.736°. The carrier ang...

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Abstract

The invention discloses a dual-redundancy flexible strapdown inertial measurement system. According to the invention, redundancy design is conducted on strapdown inertia units. Two groups of flexible strapdown inertial measurement systems are mounted on a rocket body in parallel through a vibration reduction support; each group of flexible strapdown inertial measurement system comprises three dynamically-tuned gyroscopes with two degrees of freedom, four quartz accelerometers, servo loops and I / F change-over circuits; the servo loops are matched with the dynamically-tuned gyroscopes and the quartz accelerometers. The dual-redundancy flexible strapdown inertial measurement system has the advantages as follows: the reliability and precision are increased; the operating requirements of high reliability and precision of manned space flight are met; the vibration reduction support is designed according to structure symmetry and temperature fields; collimation prisms are mounted at the symmetry positions of structures and the temperature fields, so that deformation caused by stress and temperature is efficiently prevented from affecting azimuth deviation.

Description

technical field [0001] The invention relates to a double-redundant flexible strapdown inertial measurement system, in particular to a highly reliable, high-precision and high-redundancy flexible strapdown inertial measurement system, which belongs to the technical field of inertial measurement. Background technique [0002] Manned launch vehicles are related to the lives of astronauts and the accurate and stable orbital entry of manned spacecraft. Therefore, the reliability, accuracy, and redundancy of inertial measurement devices are highly required. The existing strapdown inertial sets provide the control system with a set of incremental information of the angular velocity and apparent acceleration of the three coordinate systems of x, y, and z. If one of the measurement information fails or is out of tolerance, the control system will not be able to guide and control accurately, and the rocket will not be able to accurately send the manned spacecraft into the predetermine...

Claims

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Application Information

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IPC IPC(8): G01C21/24G01C21/18
Inventor 胡荣辉曾宪超张宏彬胡利
Owner BEIJING INST OF AEROSPACE CONTROL DEVICES
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